CN109268625A - A kind of low temperature lightweight low heat conductivity composite adiabatic structure - Google Patents
A kind of low temperature lightweight low heat conductivity composite adiabatic structure Download PDFInfo
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- CN109268625A CN109268625A CN201811409473.1A CN201811409473A CN109268625A CN 109268625 A CN109268625 A CN 109268625A CN 201811409473 A CN201811409473 A CN 201811409473A CN 109268625 A CN109268625 A CN 109268625A
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16L—PIPES; JOINTS OR FITTINGS FOR PIPES; SUPPORTS FOR PIPES, CABLES OR PROTECTIVE TUBING; MEANS FOR THERMAL INSULATION IN GENERAL
- F16L59/00—Thermal insulation in general
- F16L59/02—Shape or form of insulating materials, with or without coverings integral with the insulating materials
- F16L59/029—Shape or form of insulating materials, with or without coverings integral with the insulating materials layered
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/52—Protection, safety or emergency devices; Survival aids
- B64G1/58—Thermal protection, e.g. heat shields
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16L—PIPES; JOINTS OR FITTINGS FOR PIPES; SUPPORTS FOR PIPES, CABLES OR PROTECTIVE TUBING; MEANS FOR THERMAL INSULATION IN GENERAL
- F16L59/00—Thermal insulation in general
- F16L59/04—Arrangements using dry fillers, e.g. using slag wool which is added to the object to be insulated by pouring, spreading, spraying or the like
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Abstract
The present invention relates to a kind of low temperature lightweight low heat conductivity composite adiabatic structures, can be used in the insulation of aircraft Cryogenic tank, which is mainly made of variable density multilayer insulation material, heat barrier foam layer.The type heat insulating construction changes the layer density of multilayer insulation material using light materials such as polyimides silk screen, hollow glass microballoons as the spacer of multilayer material, to realize the purpose for reducing multilayer insulation material thermal conductivity, mitigating multilayer insulation material weight.Heat barrier foam layer can ensure that heat insulating construction has good heat insulation in atmospheric pressure environment.The type heat insulating construction has combined the heat-proof quality under vacuum environment and atmospheric pressure environment, compared to con-ventional insulation structure, the type composite adiabatic structure has the characteristics that heat-proof quality is more preferable, weight is lighter, arrangement is more flexible, to effectively solve the control problem of cryogenic propellant evaporation capacity, it can be applied to the fields such as manned space flight, deep space exploration.
Description
Technical field
The present invention relates to a kind of low temperature lightweight low heat conductivity composite adiabatic structures, belong to cryogenic propellant in-orbit storage for a long time
With management domain.
Background technique
Cryogenic propellant easily carburation by evaporation needs for the evaporation rate for reducing cryogenic propellant using heat insulating construction packet
Cryogenic propellant tank is covered, environment is reduced to the leakage heat inside tank with this.Cryogenic propellant tank is in vacuum environment and often
It is needed in pressure ring border using different heat insulating constructions.In atmospheric pressure environment, environment mainly passes through thermally conductive way to leakage heat inside tank
Diameter commonly uses foaming structure cladding tank to reduce leakage heat；And in vacuum environment, radiation leakage heat is that environment is warm to leakage inside tank
Main path, multilayer insulation material is common heat insulating construction material in vacuum environment, can be effectively reduced environment to system
In leakage heat, major defect be as the weight that increases of the multilayer number of plies significantly rises, for the aircraft of in-orbit flight,
Heat insulating construction weight, which crosses senior general, reduces the quality of payload.Cryogenic propellant tank is from ground battery to in-orbit flight
During state, the variation from atmospheric pressure environment to vacuum environment experienced, environment also occurs to the main path for leaking heat inside tank
Variation, therefore, it is necessary to two different heat insulating constructions.There is weight when two different heat insulating constructions are coated on tank surface
Amount is big, arrangement is not flexible, the disadvantages of having a single function.
Summary of the invention
The present invention is different from the conventional multilayer heat-barrier material of even density distribution, and the type heat insulating construction is mainly more by variable density
Layer heat-barrier material, heat barrier foam layer are constituted.The type heat insulating construction makees the light materials such as polyimides silk screen, hollow glass microballoon
For the spacer of multilayer material, change the layer density of multilayer insulation material, so that realizing reduces multilayer insulation material thermal conductivity, subtracts
The purpose of light multilayer insulation material weight.Heat barrier foam layer can ensure that heat insulating construction has good heat-insulated effect in atmospheric pressure environment
Fruit, while having the effect of that anti-aerodynamic heating washes away.The type heat insulating construction has combined under vacuum environment and atmospheric pressure environment
Heat-proof quality, compared to con-ventional insulation structure, which has that heat-proof quality is more preferable, weight is lighter, arrangement side
The more flexible feature of case can be applied to manned space flight, deep space to effectively solve the control problem of cryogenic propellant evaporation capacity
The fields such as detection.
What above-mentioned purpose of the invention was mainly achieved by following technical solution: a kind of low temperature lightweight low heat conductivity
Composite adiabatic structure, including variable density multilayer insulation component (I) and foam heat-insulating component (II), in which:
Variable density multilayer insulation component (I) is warm (from heat for reducing radiation leakage of the composite adiabatic structure in vacuum environment
It holds to cold end building heat)；Thermally conductive leakage heat of the foam heat-insulating component (II) for reducing composite adiabatic structure in atmospheric pressure environment, simultaneously
With protection aerodynamic heating souring；Variable density multilayer insulation component (I) is bonded with foam heat-insulating component (II).
Variable density multilayer insulation component (I), by low heat conductivity lightweight spacer (1), two-sided aluminized mylar (2) structure
At, wherein two-sided aluminized mylar (2) is attached to thermal conductivity lightweight spacer (1) two sides.
Low heat conductivity lightweight spacer (1) is porous polyimide silk screen or hollow glass microballoon.
According to the heat-insulated needs of aircraft, can be realized by adjusting the surface density of low heat conductivity lightweight spacer (1) different
The insulation of degree.
Two-sided aluminized mylar (2) leaks heat for reducing the radiation of multilayer insulation component.
Two-sided aluminized mylar (2) is polyimide film, and the two-sided aluminizer of polyimide film.
Low heat conductivity lightweight spacer (1) and two-sided aluminized mylar (2) form insulating unit, each insulating unit
Density is different, and variable density multilayer insulation component (I) is made to include: low-density layer (4), middle density layer (5), high-density layer (6), low close
Spend layer (4), middle density layer (5), high-density layer (6) random arrangement, each density layer include it is one or more mutually fit every
Hot cell；
Low heat conductivity lightweight spacer (1) and two-sided aluminized mylar (2) form insulating unit, each insulating unit
Density is different, makes variable density multilayer insulation component (I) include: low-density layer (4), middle density layer (5), high-density layer (6), each
The density of insulating unit is different, and making variable density multilayer insulation component (I) includes: low-density layer (4), middle density layer (5), high density
Layer (6), the successively distributing order from cold end to hot end are as follows: low-density layer (4), middle density layer (5), high-density layer (6).
Foam heat-insulating component (II) is that polyurethane is the foam that raw material foaming is prepared, and centre doping hollow glass is micro-
Ball.
Variable density multilayer insulation component (I) is mounted on aircraft cryogenic propellant tank outer surface i.e. cold end, foam heat-insulating
Component (II) is exposed in atmospheric environment i.e. hot end.
Compared with prior art, the present invention has the following advantages:
(1) multilayer insulation component of the invention can be effectively reduced radiation leakage of the cryogenic propellant tank in vacuum environment
Heat.
(2) shown compared with layer even density multilayer material by theoretical and test result, the present invention is more using variable density
System weight can be effectively reduced under the premise of guaranteeing heat insulation in the placement scheme of layer.
(3) present invention uses the low heat conductivities such as hollow glass microballoon or porous polyimide silk screen lightweight spacer, with biography
The nylon wire spacer of system multilayer material is compared, and can reduce the thermal conductivity of multilayer insulation component, and reduce system weight.
(4) foam heat-insulating component of the invention can reduce thermally conductive leakage heat of the composite adiabatic structure in atmospheric pressure environment, together
When have protection aerodynamic heating souring.
(5) weight of composite adiabatic structure of the invention is lighter, and arrangement is more flexible, is suitable for aerospace craft and uses,
Reduce the bearing requirements of aerospace craft；
(6) composite adiabatic structure of the present invention combines the heat-proof quality in vacuum environment and atmospheric pressure environment, utilizes foam
The strength character of insulating assembly can also play the effect that protection aerodynamic heating washes away.
(7) present invention is different from the conventional multilayer heat-barrier material of even density distribution, and the type heat insulating construction is mainly by becoming close
Spend multilayer insulation material, heat barrier foam layer is constituted.The type heat insulating construction is by the lightweights material such as polyimides silk screen, hollow glass microballoon
Expect the spacer as multilayer material, change the layer density of multilayer insulation material, to realize that reduction multilayer insulation material is thermally conductive
Rate, the purpose for mitigating multilayer insulation material weight.
(8) heat barrier foam layer can ensure that heat insulating construction has good heat insulation in atmospheric pressure environment, while have anti-
The effect that aerodynamic heating washes away.The type heat insulating construction has combined the heat-proof quality under vacuum environment and atmospheric pressure environment, compares
In con-ventional insulation structure, which has that heat-proof quality is more preferable, weight is lighter, the more flexible spy of arrangement
Point can be applied to the fields such as manned space flight, deep space exploration to effectively solve the control problem of cryogenic propellant evaporation capacity.
Detailed description of the invention
Fig. 1 is low temperature lightweight low heat conductivity composite adiabatic structure composition schematic diagram of the present invention；
Fig. 2 is thermal conductivity test result schematic diagram；
Fig. 3 is intensity test result.
Specific embodiment
The present invention is described in further detail in the following with reference to the drawings and specific embodiments:
Multi layer thermal insulation system (MLI) has important application in the field that space flight and other many are related to cryogenic fluid.This
Kind system forms very high thermal resistance to radiant heat flux using the reflection layer by layer between radiation shield panel, has under vacuum fabulous
Heat-proof quality, theoretically its equivalent thermal conductivity can be down to 10-5W/ (m.K) magnitude below.Multi layer thermal insulation system is usually used in navigating
In its device heat control system, spacecraft internal environment is isolated with the external thermal environments of acute variation, it is ensured that instrument and equipment work exists
Within the temperature range of regulation.In recent years, in terms of Cryogenic tank is heat-insulated, reentry vehicle is prevented, multilayer insulation material
It is widely used.
As shown in Figure 1, a kind of low temperature lightweight low heat conductivity composite adiabatic structure of the invention, including variable density multilayer insulation
Component (I) and foam heat-insulating component (II), in which: variable density multilayer insulation component (I) is for reducing composite adiabatic structure true
Radiation leakage heat (hot from hot end to cold end building) in Altitude；Foam heat-insulating component (II) is for reducing composite adiabatic structure normal
Thermally conductive leakage heat in pressure ring border, while there is protection aerodynamic heating souring；Variable density multilayer insulation component (I) and foam every
Hot component (II) fitting.Variable density multilayer insulation component (I), by low heat conductivity lightweight spacer (1), two-sided aluminized mylar
(2) it constitutes, wherein thermal conductivity lightweight spacer (1) and two-sided aluminized mylar (2) fluffy overlapping.Between low heat conductivity lightweight
Parting (1) is porous polyimide silk screen or hollow glass microballoon.Wherein polyimides silk screen is the preparation method comprises the following steps: by diamines, two
Acid anhydride raw material and solvent dimethyl acetamide row are mixed with to obtain polyamic acid (PAA) spinning solution, by PAA after defoaming treatment
Solution carries out spinneret, silk is frozen into coagulating bath, then cleaned in cleaner bath, forms clean PAA fiber and goes forward side by side one
Step continuously carries out drawing-off and heat treatment, then the rolled rear final polyimide fiber product of generation, porous polyamides Asia in hot stove
Amine silk screen is preferably the porous web that polyimides silk is woven into, and preferred surface density is from 10g/m3~200g/m3。
According to the heat-insulated needs of aircraft, can be realized by adjusting the surface density of low heat conductivity lightweight spacer (1) different
The insulation of degree, when cold end warm area is preferably in 20 kelvin degrees~70 kelvin degrees, close to cold end low heat conductivity lightweight
Spacer (1), which thickeies, arrives 2mm~5mm, and for changing the layer density of multilayer insulation component (I), preferably cold end is in liquid nitrogen temperature heat
Conductance≤0.015W/mK makes heat insulation more preferably.Two-sided aluminized mylar (2), for reducing the spoke of multilayer insulation component
Penetrate leakage heat.Two-sided aluminized mylar (2) is polyimide film, and the two-sided aluminizer of polyimide film.Two-sided aluminum polyester
Film (2) leaks heat for reducing the radiation of multilayer insulation component.(two-sided aluminized mylar (2) is polyimide film, thickness
At 6~20 microns, two-sided aluminizer, aluminium film thickness is preferably at 0.09~1.01 micron.
Low heat conductivity lightweight spacer (1) and two-sided aluminized mylar (2) form insulating unit, each insulating unit
Density is different, and variable density multilayer insulation component (I) is made to include: low-density layer (4), middle density layer (5), high-density layer (6), low close
Spend layer (4), middle density layer (5), high-density layer (6) random arrangement, each density layer include it is one or more mutually fit every
Hot cell；Preferred embodiment are as follows: the successively distributing order from cold end to hot end are as follows: low-density layer (4), middle density layer (5), high-density layer
(6).Preferred embodiment in low-density layer (4) are as follows: preferably every 1 cm thick includes 6~12 insulating units；It is preferred that middle density layer
(5) every 1 cm thick includes 12~18 insulating units, and every 1 cm thick of high-density layer (6) includes 18~24 heat-insulated lists
Member.
Foam heat-insulating component (II) is that polyurethane is the foam that raw material foaming is prepared, and centre doping hollow glass is micro-
Ball.Preferred foams density≤40kg/m of foam heat-insulating component (II)3, and foam heat-insulating component (II) preferably thermal conductivity≤
0.024W/mK, and preferred compressed intensity >=0.22MPa of foam heat-insulating component (II), and foam heat-insulating component (II) is excellent
Liquid nitrogen temperature thermal conductivity≤0.015W/mK, and preferred thickness >=20mm of foam heat-insulating component (II) are selected, foam heat-insulating group is made
The heat-insulating property of part (II) further increases.
One end of variable density multilayer insulation component (I) is cold end (low temperature object to be protected), the other end and foam heat-insulating
One end of component (II) is bonded, and the other end of foam heat-insulating component (II) is hot end (thermal environment).Cold end is to protect on aircraft
The low temperature object of shield, the thermal environment that hot end is exposed to by aircraft.For aircraft tank it is heat-insulated when, variable density multilayer every
Hot component (I) is mounted on aircraft cryogenic propellant tank outer surface i.e. cold end, and foam heat-insulating component (II) is exposed to big compression ring
The border hot end Zhong Ji.
Variable density multilayer insulation component (I) is mounted on cryogenic propellant tank outer surface (cold end), foam heat-insulating component
(II) (hot end) is exposed in atmospheric environment.
When cryogenic propellant tank is in vacuum environment, variable density multilayer insulation component (I) plays main heat-blocking action,
Multilayer insulation material forms very high thermal resistance to radiant heat flux, under vacuum using the reflection layer by layer between aluminizer radiation shield
With fabulous heat-proof quality.
When cryogenic propellant tank is in atmospheric pressure environment, foam heat-insulating component (II) plays main heat-blocking action, utilizes
The low feature of foamed material thermal conductivity can be effectively reduced the thermally conductive leakage heat of system, reduce the evaporation rate of cryogenic propellant.
When cryogenic propellant tank is in endoatmosphere flight environment of vehicle state, foam heat-insulating component (II) can also be played
The effect that anti-Aerodynamic Heating washes away protects internal variable density multilayer insulation component (I).
The present invention embodies in mentality of designing is integrated into vacuum environment and different type heat insulating construction in atmospheric pressure environment
For a kind of new composite structure, loss of weight design is carried out under the premise of guaranteeing insulation effect, using hollow glass microballoon or porous
The low heat conductivities lightweight spacer such as polyimides silk screen can reduce more compared with the nylon wire spacer of conventional multilayer material
The thermal conductivity of layer insulating assembly, and reduce system weight.The present invention has combined the anti-airflow scouring effect of heat insulating construction, doping
The polyurethane foam of hollow glass microballoon, it is lighter compared to traditional foaming structure quality, heat-insulating property is more preferable, and have good
Good rigidity, what is encountered when can resist aircraft flight pneumatically washes away, to protect internal variable density multistory steel structure.
If cold junction temperature be T1, hot-side temperature T2, variable density multilayer insulation component (I) with a thickness of H, foam heat-insulating group
The density of part (II) is ρ；
Meet following relationship, can be further improved the insulation rate of heat insulating construction, while guaranteeing insulation effect.
Wherein, K1Value range is 0.1~0.2, K2Value range is 8~10.
The polyurethane foam of doping hollow glass microballoon in the present invention has carried out thermal conductivity testing experiment and compression strength
Test, and be compared with the polyurethane foam of traditional hollow glass microballoon that undopes, test environment is condition of normal pressure.Fig. 2 gives
Thermal conductivity test result is gone out, a is the low-temperature thermal conductivity line of conventional polyurethanes foam, and b is the foam for adding hollow glass microballoon
Low-temperature thermal conductivity line.From figure 2 it can be seen that foam is thermally conductive after doping hollow glass microballoon compared with conventional foam
Rate is remarkably decreased, and from 11.8mW/m.K decline 2.4mW/m.K or so, reduction amplitude reaches 80% or so, significantly improves poly- ammonia
The heat-insulating property of ester foam.
Fig. 3 gives intensity test as a result, c is the foam compression strength line for adding hollow glass microballoon, and d is conventional
Polyurethane foam compression strength line.From figure 3, it can be seen that adulterating foam after hollow glass microballoon compared with conventional foam
Compression strength improve, from 0.23Mpa lifting values 0.28Mpa or so, increase rate about 20%.
Above-mentioned testing experiment shows that the foam insulation structure of the doping hollow glass microballoon used in the present invention is effectively reduced
Heat insulating construction thermal conductivity, while compression strength is improved, pneumatic scouring capability is resisted to significantly improve.
The above, optimal specific embodiment only of the invention, but scope of protection of the present invention is not limited thereto,
Anyone skilled in the art is in technical scope disclosed by the invention, and any changes or substitutions that can be easily thought of,
It should be covered by the protection scope of the present invention.
The content that description in the present invention is not described in detail belongs to the well-known technique of professional and technical personnel in the field.
Claims (10)
1. a kind of low temperature lightweight low heat conductivity composite adiabatic structure, it is characterised in that: including variable density multilayer insulation component (I) and
Foam heat-insulating component (II), in which:
Variable density multilayer insulation component (I) leaks heat for reducing radiation of the composite adiabatic structure in vacuum environment；Foam heat-insulating
Thermally conductive leakage heat of the component (II) for reducing composite adiabatic structure in atmospheric pressure environment, while there is protection aerodynamic heating to wash away work
With；Variable density multilayer insulation component (I) is bonded with foam heat-insulating component (II).
2. a kind of low temperature lightweight low heat conductivity composite adiabatic structure according to claim 1, it is characterised in that: variable density is more
Layer insulating assembly (I), is made of, wherein thermal conductivity lightweight low heat conductivity lightweight spacer (1), two-sided aluminized mylar (2)
Spacer (1) is bonded with two-sided aluminized mylar (2).
3. a kind of low temperature lightweight low heat conductivity composite adiabatic structure according to claim 2, it is characterised in that: low heat conductivity
Lightweight spacer (1) is porous polyimide silk screen or hollow glass microballoon.
4. a kind of low temperature lightweight low heat conductivity composite adiabatic structure according to claim 2, it is characterised in that: according to flight
The heat-insulated needs of device can realize different degrees of insulation by adjusting the surface density of low heat conductivity lightweight spacer (1).
5. a kind of low temperature lightweight low heat conductivity composite adiabatic structure according to claim 2, it is characterised in that: two-sided to aluminize
Polyester film (2) leaks heat for reducing the radiation of multilayer insulation component.
6. a kind of low temperature lightweight low heat conductivity composite adiabatic structure according to claim 2, it is characterised in that: two-sided to aluminize
Polyester film (2) is polyimide film, and the two-sided aluminizer of polyimide film.
7. a kind of low temperature lightweight low heat conductivity composite adiabatic structure according to claim 1, it is characterised in that: low heat conductivity
Lightweight spacer (1) and two-sided aluminized mylar (2) form insulating unit, and the density of each insulating unit is different, make to become close
Spending multilayer insulation component (I) includes: low-density layer (4), middle density layer (5), high-density layer (6), low-density layer (4), middle density
Layer (5), high-density layer (6) random arrangement, each density layer include one or more insulating units mutually to fit.
8. a kind of low temperature lightweight low heat conductivity composite adiabatic structure according to claim 1, it is characterised in that: low heat conductivity
Lightweight spacer (1) and two-sided aluminized mylar (2) form insulating unit, and the density of each insulating unit is different, make to become close
Spending multilayer insulation component (I) includes: low-density layer (4), middle density layer (5), high-density layer (6), the density of each insulating unit
Difference makes variable density multilayer insulation component (I) include: low-density layer (4), middle density layer (5), high-density layer (6), from cold end to
Hot end successively distributing order are as follows: low-density layer (4), middle density layer (5), high-density layer (6).
9. a kind of low temperature lightweight low heat conductivity composite adiabatic structure according to claim 1, it is characterised in that: foam heat-insulating
Component (II) is that polyurethane is the foam that raw material foaming is prepared, centre doping hollow glass microballoon.
10. a kind of low temperature lightweight low heat conductivity composite adiabatic structure according to claim 1, it is characterised in that: variable density
Multilayer insulation component (I) is mounted on aircraft cryogenic propellant tank outer surface i.e. cold end, and foam heat-insulating component (II) is exposed to
It is hot end in atmospheric environment.
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| CN110553969A (en) * | 2019-08-22 | 2019-12-10 | 西安交通大学 | Experimental device for measuring porous medium low temperature wicking characteristic with adjustable superheat degree |
| CN111207270A (en) * | 2020-03-11 | 2020-05-29 | 山东建筑大学 | Vacuum insulation panel containing heat radiation shielding film |
| CN111572152A (en) * | 2020-05-11 | 2020-08-25 | 航天材料及工艺研究所 | Multilayer heat insulation assembly for spacecraft and preparation method thereof |
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| CN111207270A (en) * | 2020-03-11 | 2020-05-29 | 山东建筑大学 | Vacuum insulation panel containing heat radiation shielding film |
| CN111572152A (en) * | 2020-05-11 | 2020-08-25 | 航天材料及工艺研究所 | Multilayer heat insulation assembly for spacecraft and preparation method thereof |
| CN111572152B (en) * | 2020-05-11 | 2022-08-12 | 航天材料及工艺研究所 | Multilayer heat insulation assembly for spacecraft and preparation method thereof |
| US11358375B1 (en) | 2020-11-04 | 2022-06-14 | Space Systems/Loral, Llc | Flexible micrometeoroid shield |
| CN112460915A (en) * | 2020-11-30 | 2021-03-09 | 中国运载火箭技术研究院 | Device and method for preparing deep supercooled liquid oxygen |
| CN112460915B (en) * | 2020-11-30 | 2022-06-03 | 中国运载火箭技术研究院 | Device and method for preparing deep supercooled liquid oxygen |
| CN114414622A (en) * | 2022-01-25 | 2022-04-29 | 北京卫星环境工程研究所 | Universal composite heat insulation method suitable for vacuum and normal pressure environments |
| CN114414622B (en) * | 2022-01-25 | 2024-03-19 | 北京卫星环境工程研究所 | Universal composite heat insulation method suitable for vacuum and normal pressure environment |
| CN116202015A (en) * | 2022-12-20 | 2023-06-02 | 江苏深绿新能源科技有限公司 | Multilayer heat insulation composite structure for double-wall low-temperature container and coating process thereof |
| CN116202015B (en) * | 2022-12-20 | 2024-05-31 | 江苏深绿新能源科技有限公司 | Multilayer heat insulation composite structure for double-wall low-temperature container and coating process thereof |
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